变步长时滞控制
Variable-Step Time-Delay Control for Proactive Aperiodic Spacecraft Attitude Control
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中文总结 AI 辅助
本文提出VTDC控制框架，将反馈控制与更新调度结合，通过闭式反馈律自动调节控制区间，排除芝诺行为，经航天器姿态仿真验证可行且计算负担低。
中文摘要 AI 辅助
本文提出了变步长时滞控制（Variable-step Time Delay Control, VTDC），这是一种主动非周期鲁棒控制框架，可同时解决反馈控制与控制更新调度问题，而非将控制器与触发机制视为独立组件。受Runge-Kutta积分中的自适应步长调节启发，VTDC利用局部控制误差可按实际时间步长缩放的特性。采用基于滑模流形的时滞控制，所得系统时滞误差（TDE，反映局部模型与不确定性变化）被证明与控制区间成二次有界关系。该关系支持一种闭式反馈律，可自动增大或减小后续区间以调节TDE幅值。由于调度律直接由控制器结构构建，下一次更新时间可通过代数方式确定，无需连续触发监测、未来状态预测或迭代搜索。所得变步长闭环系统被证明具有有界时间步长与步长比，排除芝诺行为，并使滑模变量一致最终有界。航天器姿态控制仿真进一步验证了该框架的实际可行性与低计算负担。
英文摘要
This paper addresses proactive aperiodic spacecraft attitude control under model uncertainty, environmental disturbances, and actuator degradation. To this end, we develop Variable step Time Delay Control (VTDC), which jointly designs robust feedback control and control-update scheduling rather than treating them as separate components. Inspired by adaptive stepsize regulation in Runge Kutta integration, VTDC structures the local control error to scale with the realized timestep. Using sliding manifold based Time Delay Control, the resulting System Time Delay Error (TDE), which reflects local model and uncertainty variations, is shown to be quadratically bounded by the control interval. This relation yields a closed form feedback law that enlarges or reduces the subsequent interval to regulate the TDE magnitude. The next update time is therefore determined algebraically without continuous trigger monitoring, future state prediction, or iterative search. The resulting variable step closed loop admits bounded timesteps and step ratios, excludes Zeno behavior, and renders the sliding variable uniformly ultimately bounded. Nonlinear spacecraft attitude control simulations demonstrate accurate tracking with low scheduling cost under representative uncertainties and disturbances.
发表机构
- Yonsei University（延世大学）
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